US20220259975A1 - Split ring seal for gas turbine engine rotor - Google Patents
Split ring seal for gas turbine engine rotor Download PDFInfo
- Publication number
- US20220259975A1 US20220259975A1 US17/177,585 US202117177585A US2022259975A1 US 20220259975 A1 US20220259975 A1 US 20220259975A1 US 202117177585 A US202117177585 A US 202117177585A US 2022259975 A1 US2022259975 A1 US 2022259975A1
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- Prior art keywords
- shaft
- inner disc
- ring
- disc
- fore
- Prior art date
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/025—Fixing blade carrying members on shafts
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
- F16J15/3268—Mounting of sealing rings
- F16J15/3272—Mounting of sealing rings the rings having a break or opening, e.g. to enable mounting on a shaft otherwise than from a shaft end
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
- F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/24—Rotors for turbines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
- F05D2240/58—Piston ring seals
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/44—Free-space packings
- F16J15/441—Free-space packings with floating ring
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/44—Free-space packings
- F16J15/441—Free-space packings with floating ring
- F16J15/442—Free-space packings with floating ring segmented
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J9/00—Piston-rings, e.g. non-metallic piston-rings, seats therefor; Ring sealings of similar construction
- F16J9/12—Details
- F16J9/14—Joint-closures
Definitions
- the application relates generally to gas turbine engine rotors and, more particularly, to seals for gas turbine engine rotors.
- stationary and rotary engine components are arranged to define flow paths in which working fluids, for example hot, expanding combustion gases and generally cooler, compressed air, are processed for the engine to operate.
- working fluids for example hot, expanding combustion gases and generally cooler, compressed air
- flow path-defining engine components are commonly affected by dimensional variations, which may result in modifications in flow path geometry having an impact on engine performance. The effects of such dimensional variations may be exacerbated as they occur to rotary components, which may vibrate in presence of non axisymmetric deformation.
- Ad hoc structural means for managing flows of working fluid that are routed in and around rotary components of the engines may be opportune.
- a gas turbine engine rotor assembly comprising: a shaft rotatable about an axis, the shaft having an outer shaft surface radially outward relative to the axis and a shaft groove radially into the outer shaft surface; a disc surrounding the shaft and rotatable with the shaft about the axis, the disc having an inner disc surface extending axially and defining an inner disc diameter at an axial location of the inner disc surface, the inner disc surface having a disc tapering profile extending circumferentially around the shaft groove and axially away from and radially inwardly of the inner disc diameter, the shaft and the disc together defining a gap circumscribed outwardly by the inner disc diameter and inwardly by the outer shaft surface; and a seal including a split ring fitted into the shaft groove and rotatable with the shaft about the axis, the split ring having an outer ring surface having a ring tapering profile complementary to the disc tapering profile, the split ring resiliently expandable radi
- a gas turbine engine comprising: a shaft rotatable about an axis, the shaft having an outer shaft surface radially outward relative to the axis and a shaft groove radially into the outer shaft surface; a disc surrounding the shaft and rotatable with the shaft about the axis, the disc having an inner disc surface extending axially and defining an inner disc diameter at an axial location of the inner disc surface, the inner disc surface having a ramped disc profile extending circumferentially around the shaft groove and axially away from and radially inwardly of the inner disc diameter, the shaft and the disc together defining a gap circumscribed outwardly by the inner disc diameter and inwardly by the outer shaft surface; and a seal including a split ring fitted into the shaft groove and rotatable with the shaft about the axis, the split ring having an outer ring surface having a ramped ring profile complementary to the ramped disc profile, the split ring resiliently expandable radi
- FIG. 1 is a schematic cross-sectional view of a gas turbine engine
- FIG. 2 is a partial schematic cross-sectional view of a compressor section of the gas turbine engine of FIG. 1 ;
- FIG. 3 is a partial cross-sectional view of a rotor of the compressor section of FIG. 2 ;
- FIG. 4 is a perspective view of a disc and a seal of the rotor of FIG. 3 ;
- FIG. 5A is a close up view of a split joint of the seal of FIG. 4 ;
- FIGS. 5B and 5C are close up views of alternate implementations of the split joint of FIG. 5A ;
- FIG. 6A is a close up view of a channel of the seal of FIG. 4 ;
- FIG. 6B is an alternate implementation of the channel of the seal of FIG. 4 ;
- FIG. 7 is an elevation view of two seals corresponding to alternate implementations of the seal of FIG. 4 shown keyed at an angle to one another, and
- FIG. 8 is a partial cross-sectional view of an alternate implementation of the rotor of FIG. 3 including a shaft fitted with two seals corresponding to alternate implementations of the seal of FIG. 4 .
- FIG. 1 illustrates a gas turbine engine 10 of a type preferably provided for use in subsonic flight, generally comprising in serial flow communication a fan 12 through which ambient air is propelled, a compressor section 14 for pressurizing the air, a combustor 16 in which the pressured (or compressed) air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section 18 for extracting energy from the combustion gases.
- a shaft 20 of the engine 10 extends along a center line axis CL, surrounded by a casing 30 .
- a high-pressure, downstream portion of the compressor section 14 is presented in FIG. 2 as one exemplary implementation of the present technology, and will be referred to henceforth as a compressor 14 .
- the compressor 14 generally includes a stator (or shroud) 40 disposed inside the casing 30 and a rotor 50 surrounded by the stator 40 .
- the rotor 50 includes a shaft 60 rotatable about a rotation axis R of the engine 10 , in this case collinear to the center line axis CL.
- the rotor 50 also includes a plurality of discs 70 rotatable with the shaft 60 as the shaft 60 rotates about the axis R.
- Each disc discs 70 define an inner (or central) bore 70 a via which the shaft 60 is received. From the bore 70 a , each disc 70 extends radially outwardly relative to the axis R to a rim 80 .
- the rim 80 is provided with radially-extending vanes 90 .
- the discs 70 are disposed consecutively such that their respective rims 80 form an inner circumferential boundary of an axial compression flow path F c of the compressor 14 , which is circumscribed outwardly by the stator 40 .
- a hub 82 extends radially inwardly from the rim 80 of a downstream-most disc 70 to the shaft 60 , separating an engine cavity A of the engine from a rotor cavity B of the rotor 50 .
- the rotor cavity B extends axially to a foremost hub (not shown) of the rotor 50 .
- the hub 82 may be referred to as rearmost (or aft) hub 82 .
- the rotor cavity B surrounds the shaft 60 and, between the fore hub and the aft hub 82 , the rotor cavity B is circumscribed outwardly by the rims 80 of the discs 70 .
- Each disc 70 may thus be said to have a portion defined between its corresponding rim 80 and bore 70 a that extends radially inwardly into the rotor cavity B.
- the bore 70 a of each disc 70 defines a radial gap G ( FIG. 3 ) with a corresponding portion of the shaft 60 received thereby.
- a flow of air is progressively compressed along the axial compression flow path F c and routed downstream therefrom to the combustor 16 . Downstream of the axial compression flow path F c , the air is thus at a high pressure and also at a greater temperature due to heat radiation and hot bleeding air coming from the vicinity of the combustor 16 .
- Such conditions may be present for example inside the engine cavity A, leading to a flow of hot, pressurized air F A flowing into the rotor 50 , and to lesser degrees inside the rotor cavity B, causing further air displacement.
- the pressure and temperature between any two consecutive discs 70 is conversely greater the closer the discs are to the hub 82 (and to the engine cavity A).
- each disc 70 forms a part of an axial flow path across the discs 70 .
- the radial gap G of at least one of the discs 70 is fitted with a seal 100 arranged to block or at least hinder fluid communication across such discs 70 .
- Such discs 70 and their corresponding seal 100 may be said to partition the rotor cavity B.
- One such disc is shown at 70 ′.
- a portion of the rotor cavity B located aft of the disc 70 ′ having the seal 100 is referred to as a first cavity B 1
- a portion of the rotor cavity B located fore of the disc 70 ′ is referred to as a second cavity B 2 .
- Such cavities may be referred to as portions of a secondary air system of the engine 10 .
- a flow of hot, pressurized air F B1 enters the secondary air system in the rotor 50 aft of the seal 100 , for instance via gaps in the inner circumferential boundary of the flow path F c located aft of the first cavity B 1 .
- the rotor 50 can direct or promote a radial flow F R of hot air inside the first cavity B 1 , for example to heat up surrounding rims 80 and vanes 90 .
- a flow of air F B2 of cooler temperature and lower pressure relative to the flow F B1 may form into the bore 70 a , flowing axially from the second cavity B 2 and radially inwardly from inside the bore 70 a to an inner cavity C of the shaft 60 via openings defined in the shaft 60 fore of the seal 100 .
- the seal 100 may be said to be pressured on its fore side facing the second cavity B 2 .
- an axial flow of hot, pressured air referred to henceforth as a gap flow F G , occurs axially from the first cavity B 1 across the bore 70 a of the disc 70 ′ and the corresponding seal 100 via the gap G.
- the inner cavity C of the shaft 60 is a hollow interior surrounded by an interior shaft surface 60 a of a generally cylindrical shape extending axially about a shaft axis that is coaxial with respect to the axis R.
- an exterior shaft surface 60 b follows the interior shaft surface 60 a , albeit defining portions having different radial profiles.
- the exterior shaft surface 60 b includes a portion referred to as an outer shaft surface 62 received by the disc bore 70 a .
- the outer shaft surface 62 has an outer diameter that is greater than that of an aft portion of the exterior shaft surface 60 b located aft of the disc 70 ′.
- the shaft 60 also includes an annular shaft groove 64 defined radially inwardly into the outer shaft surface 62 .
- the shaft groove 64 has an axial dimension (or width) and a radial dimension (or depth) sized for receiving the seal 100 , as will be described hereinbelow.
- the width of the shaft groove 64 is defined axially between mutually facing walls (or surfaces) 64 a , 64 b of the shaft groove 64 , namely a fore groove wall 64 a and an aft groove wall 64 b .
- the depth of the shaft groove 64 is defined radially between the outer shaft surface 62 and a bottom groove surface 64 c of the shaft groove 64 .
- the outer shaft surface 62 is circumscribed by diameters of different sizes, namely by a greater diameter on an aft side of the shaft groove 64 compared to that on the opposite side.
- the aft groove wall 64 b is radially taller than the fore groove wall 64 a .
- the shaft groove 64 may be said to be deeper adjacent to the aft groove wall 64 b than adjacent to the fore groove wall 64 a .
- the disc 70 ′ and the shaft 60 are arranged relative to one another such that the gap G has a similar radial size immediately fore and aft of the shaft groove 64 .
- the outer shaft surface 62 tapers as it extends axially toward the aft side of the shaft groove 64 and/or tapers as it extends axially away from the fore side of the shaft groove 64 .
- the outer shaft surface 62 is cylindrical on either side of the shaft groove 64 , i.e., circumscribed by a same size diameter.
- the outer shaft surface 62 is circumscribed by two different size diameters on either side of the shaft groove 64 . For instance, in the depicted embodiment, the diameter on the aft side is greater than that on the fore side.
- a side of the shaft groove 64 circumscribed by a greater diameter may be referred to as a load-bearing side of the shaft groove 64 , corresponding to a portion of the shaft 60 adapted to be axially loaded via the seal 100 as will be described hereinbelow.
- a portion (or disc projection) 70 b of the disc 70 projects axially.
- Such disc projection 70 b extends to an aft disc end 70 c of the disc 70 ′.
- the disc 70 ′ defines an inner disc surface 72 forming an aft portion of the bore 70 a .
- the inner disc surface 72 extends fore relatively to the aft disc end 70 c , from a nearby aft end 72 b to a fore end 72 a located adjacent to an annular cavity of the disc 70 ′.
- the disc projection 70 b is sized and arranged relative to the shaft 60 such that the inner disc surface 72 axially overlaps the shaft groove 64 , thereby circumscribing the gap G on either side of the shaft groove 64 .
- the rotor 50 will exhibit some degree of geometric variability, which may occur due to thermal expansion of rotor components and/or to built-in allowances.
- the shaft 60 and the disc 70 ′ despite being rotatable together about the axis R, can become temporarily displaced relative to one another in either axial direction relative to the axis R, for example during take off and/or climb, or during descent and/or landing.
- Such axial movement occurs in a range of movement defined between a first axial position and a second axial position, here respectively represented as first 60 ′ and second 60 ′′ axial positions of the shaft 60 relative to the disc 70 ′.
- the inner disc surface 72 is sized to overhang the outer shaft surface 62 on either side of the shaft groove 72 such that the shaft groove 64 is surrounded by a portion of the inner disc surface 72 in each of the first and second axial positions 60 ′, 60 ′′.
- Such portion of the inner disc surface 72 is a ramped disc profile 74 , i.e., a shape extending radially relative to the axis R as it extends axially relative to the axis R.
- the ramped disc profile 74 is arranged to be cooperable with a corresponding profile of the seal 100 so as to directionally load the shaft 60 via the seal 100 in an axial loading direction upon the seal 100 extending across the gap G from inside the shaft groove 64 .
- the ramped disc profile 74 ramps radially outwardly relative to the axis R as it extends in one axial direction relative to a central bore axis of the bore 70 a (here represented by the axis R coaxial thereto), this one direction corresponding to the axial loading direction.
- the ramped disc profile 74 is a tapering profile which tapers at a taper angle G relative to the central bore axis (or axis R).
- the ramped disc profile 74 has fore 74 a and aft ends 74 b and tapers as it extends from the aft end 74 b to the fore end 74 a .
- the axial loading direction is the aft direction.
- the ramped disc profile 74 can be configured such that the axial loading direction corresponds to an upstream direction, i.e., a direction away from a first cavity toward a second cavity exhibiting a positive pressure differential relative to the first cavity, as is the case for the cavity B 1 relative to the cavity B 2 . Absent directional loading of the shaft 60 via the seal 100 , the pressure differential may displace the seal 100 relative to the shaft groove 64 and to the inner disc surface 72 , for example in an axial direction and/or even cocked at an angle to a radial direction relative to the axis R.
- Such misplacement of the seal 100 can open up circumferentially asymmetrical leakage paths outward and/or inward the seal 100 , i.e., into the gap G and/or the shaft groove 64 around the seal 100 .
- the seal 100 can be provided in the form of a split ring seal 100 , i.e., an annular body having a split (or split joint) along its circumference. Near the split, the gap flow F G may exhibit singularities resulting in a circumferentially asymmetrical heat transfer along the shaft 60 on either side of the shaft groove 64 , which may be further exacerbated upon the seal 100 being misplaced.
- such asymmetrical flow conditions can induce thermal bowing of the shaft 60 which, in turn, may induce vibration of the rotor 50 and of other elements of the engine 10 mechanically linked thereto.
- Axially loading the shaft 60 via the seal 100 axially positions the seal 100 relative to the shaft groove 64 and hence relative to gap-defining surfaces of the rotor 50 nearby the shaft groove 60 such that the gap flow F G is circumferentially balanced.
- Axially positioning the seal 100 against either wall 64 a , 64 b of the shaft groove 64 loads the shaft 60 .
- Such positioning of the seal 100 may correspond to a rated axial position of the seal 100 for a given operating condition of the engine 10 and/or a given axial position 60 ′, 60 ′′ of the shaft 60 relative to the disc 70 ′.
- the exemplary seal 100 has a ring-like body extending circumferentially about a ring axis and axially relative to the ring axis between fore and aft ring sides 102 a , 102 b .
- the seal 100 has an inner ring surface 102 c radially inward the ring axis between the ring sides 102 , 102 b .
- An outer ring surface 102 d of the seal 100 joins the ring sides 102 a , 102 b opposite the inner ring surface 102 c .
- At least a portion of the outer ring surface 102 d is shaped complementarily to the ramped disc profile 74 and may thus be referred to as a ramped ring profile 104 of the seal 100 .
- Such complementarity between the ramped disc profile 74 and the ramped ring profile 104 results in the ramped disc profile 74 imparting a normal force having a radial component and an axial component onto the ramped ring profile 104 upon a radial force urging the ramped ring profile 104 radially outwardly and against the ramped disc profile 74 .
- the disc 70 ′ and the seal 100 are sized and arranged relative to one another such that in operation, as the engine 10 operates and the disc 70 ′ expands radially outwardly due to a given centrifugal force and heating, the seal 100 expands radially outwardly under the given centrifugal force so as to load the ramped ring profile 104 against the ramped ring profile 74 of the disc 70 ′.
- Such loading of the ramped ring profile 104 against the ramped disc profile 74 will also occur upon the seal 100 moving axially with the shaft 60 relative to the disc 70 ′ in a direction opposite to the axial loading direction.
- the axial component of the normal force resulting from such loading of the ramped ring profile 104 against the ramped ring profile 74 will induce some axial movement of the seal 100 relative to the disc 70 ′ in the axial loading direction, to the extent allowed by the shaft groove 64 .
- the ramped ring profile 104 has a shape extending radially relative to the axis R as it extends axially relative to the axis R.
- the ramped ring profile 104 is arranged to be cooperable with the ramped disc profile 74 so as to directionally load the shaft 60 via the seal 100 in the axial loading direction upon the seal 100 extending across the gap G from inside the shaft groove 64 .
- the ramped ring profile 104 ramps radially outwardly relative to the axis R as it extends in the axial loading direction relative to the ring axis (here represented by the axis R coaxial thereto).
- the ramped ring profile 104 is a tapering profile which tapers at a taper angle relative to the ring axis (or the axis R), corresponding to the taper angle ⁇ of the ramp disc profile 104 .
- the ramped ring profile 104 has fore 104 a and aft ends 104 b and tapers as it extends from the aft end 104 b to the fore end 104 a .
- the ramp disc profile 104 can be described as a frustoconical shape, of which the fore 104 a and aft 104 b ends form first and second peripheral edges.
- An axial distance between the fore 104 a and aft 104 b ends defines a ring tapering length of the ramp disc profile 104 (or of the frustoconical shape).
- a disc tapering length defined between the fore 74 a and aft 74 b ends is greater than the ring tapering length.
- Such difference in tapering lengths can be set to be at least equal to an axial distance between the first and second axial positions 60 , 60 ′, i.e., the range of motion of the shaft 60 with the seal 100 relative to the disc 70 ′, such that cooperation between the seal 100 and the disc 70 ′ can occur across the range of motion.
- the axial loading direction is upstream, i.e., away from the cavity B 2 and toward the cavity B 1 , and hence toward positive pressure and temperature gradients.
- Configuring the axial loading direction to be upstream (or aft) as opposed to downstream (or fore) can contribute to sealing performance, in some cases mitigating the extent and/or asymmetry of the heat transfer occurring in the shaft 60 downstream of the shaft groove 64 via the gap flow F G .
- the rotor 50 is arranged for the axial loading direction to be downstream.
- the ring sides 102 a , 102 b and the inner ring surface 102 c together define an inner ring shape of the seal 100 shaped complementarily to (or receivable by) the shaft groove 64 .
- the inner ring shape of the seal 100 conforms to a bottom (or radially inner) shape of the shaft groove 64 such that the seal 100 may be seated into the shaft groove 64 .
- the seal 100 has an axial dimension (or width) and a radial dimension (or thickness) sized to be receivable by the shaft groove 64 .
- the width of the seal 100 is defined axially between mutually facing walls (or surfaces) 64 a , 64 b of the shaft groove 64 , namely a fore groove wall 64 a and an aft groove wall 64 b .
- the thickness of the seal 100 is defined radially between the inner ring surface 102 c and the outer ring surface 102 d , and may be described as a difference between diameters respectively circumscribing the seal 100 inwardly and outwardly.
- the seal 100 can be of a split ring type in some embodiments, i.e., a construction allowing resilient, radial expansion of the seal 100 under radial loading.
- the seal 100 can thus be constructed of a resilient, strong and heat resistant material, such as for example metals, metallic alloys and metal matrix composites.
- the seal 100 is expandable radially from a nominal (or baseline) diameter ⁇ of the seal 100 .
- the diameter ⁇ corresponds to an inner disc diameter defined by the inner disc surface 72 in the ramped disc profile 74 at a location between the ends 74 a , 74 b , respectively defining fore and aft inner disc diameters.
- the seal 100 Upon the shaft 60 being positioned at the first axial location 60 ′ with the seal 100 relative to the disc 70 ′, the seal 100 is seated in the shaft groove 64 and extends radially outwardly across the gap G to the diameter ⁇ . In the first axial position 60 ′, the aft end 104 b of the ramped ring profile 104 is circumscribed by the diameter ⁇ .
- the seal 100 is radially expandable to a diameter defined by the ramped disc profile 74 at a location aft of the the diameter ⁇ , in this case the aft inner disc diameter at the aft end 74 b .
- the seal 100 is rotatable with the shaft 60 so as to expanded radially outwardly to the aft inner disc diameter, thereby closing the gap G.
- moving the shaft 60 with the seal 100 from the second axial position 60 ′′ to the first axial position 60 ′ urges the seal 100 to constrict radially to the diameter ⁇ .
- radial deformation of the disc 70 ′ will cause the size of the bore 70 a (and thus of the diameters of the inner disc surface 72 ) to change.
- Narrowing of the bore 70 a may thus urge the seal 100 to constrict radially and/or to move toward the axial loading direction and, conversely, widening of the bore 70 b may allow the seal 100 to radially expand and/or to move in the direction opposite to the axial loading direction.
- the seal 100 is seated (or bottomed out) into the shaft groove 64 .
- the shaft groove 64 is sized so as to conform to the inner shape of the seal 100 upon the seal 100 being constricted radially to a diameter defined by the ramped disc profile 74 at a location fore of the diameter ⁇ , such as the fore inner disc diameter at the fore end 74 a .
- the nominal diameter ⁇ of the seal 100 corresponds to the fore inner disc diameter.
- either one or both of the ramped disc profile 74 and the ramped ring profile 104 can differ in shape, so long as a suitable geometric complementarity is provided.
- the ramped disc profile and the ramped ring profile can taper at slightly different angles or be locally non-congruent. Such a difference in taper angle may for example be in a range of 0.5 to 4 degrees.
- the embodiment of the seal 100 shown in FIG. 4 is of a split ring type, i.e., a seal having a split joint 110 .
- the seal (or split ring) 100 has a pair of mutually overlapped end portions (or ends) 112 , 114 together defining the split joint 110 , and a ring-like arcuate portion 116 extending between the ends 112 , 114 .
- the seal 100 is also provided with a channel 120 at a location diametrically opposite to the split joint 110 along the arcuate portion 116 .
- the channel 120 is defined into the inner ring surface 102 d and extends axially through the arcuate portion 116 .
- the split joint 110 and the channel 120 together form a diametrically-balanced axial flow path across the seal 100 via the split joint 110 and the channel 120 upon the seal 100 conforming to a certain outer diameter.
- the ends 112 , 114 are provided with complementary shapes being distensible to and from one another to allow the seal 100 to resiliently deform, whether by constriction or expansion. Constricting the seal 110 reduces a size of a joint flow path defined by the seal joint 110 and, conversely, expanding the seal 100 increases the size of the joint flow path.
- the channel 120 is sized, shaped and positioned relative to the split joint 110 such that a channel flow path of the channel 120 corresponds to the joint flow path upon the seal 100 conforming to an outer diameter referred to as a graded diameter, which may be the nominal diameter ⁇ in certain embodiments.
- a graded diameter which may be the nominal diameter ⁇ in certain embodiments.
- the seal 100 is radially expandable to conform to the graded diameter.
- the seal 100 is radially constrictable to conform to the graded diameter.
- the seal 100 is provided with features to minimize fretting.
- at least some of the edges at the ends 112 , 114 of the split joint 110 can be shaped (e.g., dulled, rounded off or chamfered) to mitigate stress concentration upon frictional engagement occurring with the shaft 60 , the disc 70 ′ or with an opposite one of the ends 112 , 114 .
- at least some of the edges of the seal 100 located circumferentially between the ends 112 , 114 can be shaped to minimize fretting.
- edges include the edges joining the fore and aft ring sides 102 a , 102 b to the ramped ring surface 104 , which are curved, and the edges adjacent to the inner ring surface 102 c in this case being chamfered.
- the seal 100 is constructed of an inherently low-friction material selected so as to minimize fretting.
- the seal 100 can also be provided with a low-friction coating, for instance on portions of the seal 100 deemed prone to fretting.
- suitable low-friction coating can be provided on portions of the disc bore 70 a and/or portions of the shaft 60 prone to frictionally engage with the seal 100 , whether in use or during assembly.
- a distance ⁇ is shown, schematically representing a distance between mutually-opposing surfaces of the ends 112 , 114 upon the outer diameter of the seal 100 corresponding to the nominal diameter ⁇ .
- the seal 100 is constrictable to a narrow diameter and expandable to a wide diameter.
- the narrow diameter corresponds to the fore inner disc diameter, at which the ends 112 , 114 are interlocked, with a distance therebetween being than the distance ⁇ .
- the wide diameter corresponds to the aft inner disc diameter, at which the ends are spaced by a distance greater than the distance ⁇ .
- the ends 112 , 114 have axially-extending overlapping surfaces 112 a , 114 a .
- the ends 112 , 114 have radially-extending overlapping surfaces 112 b , 114 b .
- the ends 112 , 114 each have axially-extending 112 a , 114 a and axially-extending 112 b , 114 b overlapping surfaces.
- the channel 120 may adopt an arcuate shape, although other shapes are contemplated. As shown in FIG.
- the channel 120 may be formed of a plurality of openings 120 a , 120 b distributed along a periphery of the outer ring surface 102 d .
- the shape and distribution of the openings 120 a , 120 b may vary. More than two openings 120 a , 120 b may also be provided.
- the rotor 50 can be provided with a plurality of seals, including at least one additional seal 100 ′ fitted to shaft 60 at a location fore of the seal 100 .
- the shaft 60 has a foremost shaft groove 64 ′ located between a fore end of the outer shaft surface 62 and the shaft groove 64 .
- the at least one seal 100 ′ can thus be a foremost seal 100 ′ fitted into the foremost shaft groove 64 ′.
- the seal 100 and the foremost seal 100 ′ can be fitted in the corresponding shaft grooves 64 , 64 ′ such that they are respectively expandable into the gap G at an azimuthal angle ⁇ to one another, for example 90 degrees.
- the seals 100 , 100 ′ can be clocked apart to render a flow path formed across the seals 100 , 100 ′ tortuous.
- a split joint 110 ′ and a channel 120 ′ of the foremost seal 100 ′ are respectively oriented (or clocked) at the azimuthal angle ⁇ relative to the split joint 110 and the channel 120 of the seal 100 .
- a flow path formed across the plurality of seals can be said to be indirect.
- only one of the seal 100 and the foremost seal 100 ′ is provided with a channel 120 .
- one or both of the seals 100 , 100 ′ is provided with an anti-rotational feature 130 , 130 ′ cooperable with (or keyable into) a complementary anti-rotational feature 66 associated with the corresponding shaft groove 64 , 64 ′.
- the anti-rotational feature 66 of each groove 64 , 64 ′ can arranged such the seals 100 , 100 ′ are at the azimuthal angle ⁇ upon keying into their corresponding shaft grooves 64 , 64 ′.
- FIG. 8 there is shown an exemplary embodiment of the rotor 50 in which the shaft 60 is fitted with two seals 100 , 100 ′.
- the shaft groove 64 is fitted with the seal 100
- the shaft 60 also has another groove 64 ′ spaced axially relative to the groove 64 and fitted with the seal 100 ′.
- the grooves 64 , 64 ′ are respectively located proximate to an aft end and a fore end of the outer shaft surface 64 , and thus may be referred to as an aft groove 64 and a foremost groove 64 ′.
- the seals 100 , 100 ′ may be referred to as an aft seal 100 and a foremost seal 100 ′.
- the inner disc surface 72 includes a foremost ramped disc profile 74 ′ which defines a foremost inner disc diameter close to a fore end of the inner disc surface 72 .
- the foremost ramped disc profile 74 ′ ramps (or in this case tapers) in a direction opposite to the direction in which the (aft) ramped disc profile 74 tapers.
- the foremost seal 100 ′ has a foremost ramped ring profile 104 ′ cooperable with the foremost ramped disc profile 74 ′ to directionally load the shaft 60 in an axial loading direction opposite to that associated with the aft seal 100 .
- the foremost ramped ring profile 74 ′ tapers away from the foremost inner disc diameter.
- the disc 70 ′ can cooperate with either seal 100 , 100 ′ upon the shaft 60 moving axially relative to the disc 70 ′ to axially load the shaft 60 via the one seal 100 , 100 ′ whose axial loading direction is opposite to the movement of the shaft 60 . It shall be noted that during assembly, the shaft 60 is fitted with the seals 100 , 100 ′ and received therewith by the bore 70 a from the aft end 70 c of the disc 70 ′.
- the depth of the foremost shaft groove 64 ′ is sized to be sufficient (or deep enough) for the seal 100 ′ to radially collapse clear of the aft ramped disc profile 74 as the seal 100 ′ moves axially with the shaft 60 toward the foremost ramped disc profile 74 ′.
- the seals 100 , 100 ′ are mirror images of one another and the foremost groove 64 ′ is deeper than the aft groove 64 , although it is contemplated that the aft groove 64 could have a matching depth.
- the rotor 50 may correspond, mutatis mutandis, to any other rotor of a gas turbine engine having concentric rotor parts defining a radial gap therebetween in fluid communication between cavities of the rotor at different pressures.
- Such rotors may for example be in the turbine section 18 or in an accessory gearbox of the engine 10 .
- Yet further modifications could be implemented by a person of ordinary skill in the art in view of the present disclosure, which modifications would be within the scope of the present technology.
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- The application relates generally to gas turbine engine rotors and, more particularly, to seals for gas turbine engine rotors.
- In gas turbine engines, stationary and rotary engine components are arranged to define flow paths in which working fluids, for example hot, expanding combustion gases and generally cooler, compressed air, are processed for the engine to operate. Due to the high-pressure, high-temperature conditions in play, flow path-defining engine components are commonly affected by dimensional variations, which may result in modifications in flow path geometry having an impact on engine performance. The effects of such dimensional variations may be exacerbated as they occur to rotary components, which may vibrate in presence of non axisymmetric deformation. Ad hoc structural means for managing flows of working fluid that are routed in and around rotary components of the engines may be opportune.
- In an aspect of the present technology, there is provided a gas turbine engine rotor assembly, comprising: a shaft rotatable about an axis, the shaft having an outer shaft surface radially outward relative to the axis and a shaft groove radially into the outer shaft surface; a disc surrounding the shaft and rotatable with the shaft about the axis, the disc having an inner disc surface extending axially and defining an inner disc diameter at an axial location of the inner disc surface, the inner disc surface having a disc tapering profile extending circumferentially around the shaft groove and axially away from and radially inwardly of the inner disc diameter, the shaft and the disc together defining a gap circumscribed outwardly by the inner disc diameter and inwardly by the outer shaft surface; and a seal including a split ring fitted into the shaft groove and rotatable with the shaft about the axis, the split ring having an outer ring surface having a ring tapering profile complementary to the disc tapering profile, the split ring resiliently expandable radially in the gap to the inner disc diameter, the disc tapering profile cooperable with the ring tapering profile to axially load the shaft via the split ring upon the split ring being expanded across the gap.
- In another aspect of the present technology, there is provided a seal for a gas turbine engine rotor disc, comprising: a split ring including a pair of mutually overlapped end portions together defining a split joint and an arcuate portion extending circumferentially about an axis from a first end of the end portions to a second end of the end portions, the arcuate portion having: first and second sides facing axially away from one another relative to the axis; an outer ring surface joining the first and second sides, the outer ring surface having a frustoconical shape circumscribed by a first peripheral edge proximate to the first side and by a second peripheral edge proximate to the second side, the second peripheral edge being longer than the first peripheral edge; an inner ring surface radially inward relative to the axis and extending axially between the first and second sides, and a channel defined into the inner ring surface at a location diametrically opposite to the split joint, the channel extending axially through the arcuate portion; the split ring resiliently expandable radially outwardly under centrifugal force relative to the axis to distance the end portions such that the first and second peripheral edges conform to a frustoconical shape of the gas turbine engine rotor disc.
- In yet another aspect of the present technology, there is provided a gas turbine engine, comprising: a shaft rotatable about an axis, the shaft having an outer shaft surface radially outward relative to the axis and a shaft groove radially into the outer shaft surface; a disc surrounding the shaft and rotatable with the shaft about the axis, the disc having an inner disc surface extending axially and defining an inner disc diameter at an axial location of the inner disc surface, the inner disc surface having a ramped disc profile extending circumferentially around the shaft groove and axially away from and radially inwardly of the inner disc diameter, the shaft and the disc together defining a gap circumscribed outwardly by the inner disc diameter and inwardly by the outer shaft surface; and a seal including a split ring fitted into the shaft groove and rotatable with the shaft about the axis, the split ring having an outer ring surface having a ramped ring profile complementary to the ramped disc profile, the split ring resiliently expandable radially in the gap to the inner disc diameter, the ramped disc profile cooperable with the ramped ring profile to axially load the shaft via the split ring upon the split ring being expanded across the gap.
- Reference is now made to the accompanying figures in which:
-
FIG. 1 is a schematic cross-sectional view of a gas turbine engine; -
FIG. 2 is a partial schematic cross-sectional view of a compressor section of the gas turbine engine ofFIG. 1 ; -
FIG. 3 is a partial cross-sectional view of a rotor of the compressor section ofFIG. 2 ; -
FIG. 4 is a perspective view of a disc and a seal of the rotor ofFIG. 3 ; -
FIG. 5A is a close up view of a split joint of the seal ofFIG. 4 ; -
FIGS. 5B and 5C are close up views of alternate implementations of the split joint ofFIG. 5A ; -
FIG. 6A is a close up view of a channel of the seal ofFIG. 4 ; -
FIG. 6B is an alternate implementation of the channel of the seal ofFIG. 4 ; -
FIG. 7 is an elevation view of two seals corresponding to alternate implementations of the seal ofFIG. 4 shown keyed at an angle to one another, and -
FIG. 8 is a partial cross-sectional view of an alternate implementation of the rotor ofFIG. 3 including a shaft fitted with two seals corresponding to alternate implementations of the seal ofFIG. 4 . -
FIG. 1 illustrates agas turbine engine 10 of a type preferably provided for use in subsonic flight, generally comprising in serial flow communication afan 12 through which ambient air is propelled, acompressor section 14 for pressurizing the air, acombustor 16 in which the pressured (or compressed) air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and aturbine section 18 for extracting energy from the combustion gases. Ashaft 20 of theengine 10 extends along a center line axis CL, surrounded by acasing 30. Shown at II, a high-pressure, downstream portion of thecompressor section 14 is presented inFIG. 2 as one exemplary implementation of the present technology, and will be referred to henceforth as acompressor 14. Thecompressor 14 generally includes a stator (or shroud) 40 disposed inside thecasing 30 and arotor 50 surrounded by thestator 40. - Referring to
FIG. 2 , therotor 50 includes ashaft 60 rotatable about a rotation axis R of theengine 10, in this case collinear to the center line axis CL. Therotor 50 also includes a plurality ofdiscs 70 rotatable with theshaft 60 as theshaft 60 rotates about the axis R. Eachdisc discs 70 define an inner (or central)bore 70 a via which theshaft 60 is received. From thebore 70 a, eachdisc 70 extends radially outwardly relative to the axis R to arim 80. Therim 80 is provided with radially-extendingvanes 90. Thediscs 70 are disposed consecutively such that theirrespective rims 80 form an inner circumferential boundary of an axial compression flow path Fc of thecompressor 14, which is circumscribed outwardly by thestator 40. Ahub 82 extends radially inwardly from therim 80 of adownstream-most disc 70 to theshaft 60, separating an engine cavity A of the engine from a rotor cavity B of therotor 50. Fore of thehub 82, the rotor cavity B extends axially to a foremost hub (not shown) of therotor 50. Hence, thehub 82 may be referred to as rearmost (or aft)hub 82. The rotor cavity B surrounds theshaft 60 and, between the fore hub and theaft hub 82, the rotor cavity B is circumscribed outwardly by therims 80 of thediscs 70. Eachdisc 70 may thus be said to have a portion defined between itscorresponding rim 80 and bore 70 a that extends radially inwardly into the rotor cavity B. Thebore 70 a of eachdisc 70 defines a radial gap G (FIG. 3 ) with a corresponding portion of theshaft 60 received thereby. - A flow of air is progressively compressed along the axial compression flow path Fc and routed downstream therefrom to the
combustor 16. Downstream of the axial compression flow path Fc, the air is thus at a high pressure and also at a greater temperature due to heat radiation and hot bleeding air coming from the vicinity of thecombustor 16. Such conditions may be present for example inside the engine cavity A, leading to a flow of hot, pressurized air FA flowing into therotor 50, and to lesser degrees inside the rotor cavity B, causing further air displacement. Inside the rotor cavity B, the pressure and temperature between any twoconsecutive discs 70 is conversely greater the closer the discs are to the hub 82 (and to the engine cavity A). The radial gap G of eachdisc 70 forms a part of an axial flow path across thediscs 70. The radial gap G of at least one of thediscs 70 is fitted with aseal 100 arranged to block or at least hinder fluid communication acrosssuch discs 70.Such discs 70 and theircorresponding seal 100 may be said to partition the rotor cavity B. One such disc is shown at 70′. A portion of the rotor cavity B located aft of thedisc 70′ having theseal 100 is referred to as a first cavity B1, and a portion of the rotor cavity B located fore of thedisc 70′ is referred to as a second cavity B2. Such cavities may be referred to as portions of a secondary air system of theengine 10. A flow of hot, pressurized air FB1 enters the secondary air system in therotor 50 aft of theseal 100, for instance via gaps in the inner circumferential boundary of the flow path Fc located aft of the first cavity B1. By this arrangement, therotor 50 can direct or promote a radial flow FR of hot air inside the first cavity B1, for example to heat up surroundingrims 80 and vanes 90. Fore of theseal 100, a flow of air FB2 of cooler temperature and lower pressure relative to the flow FB1, may form into thebore 70 a, flowing axially from the second cavity B2 and radially inwardly from inside thebore 70 a to an inner cavity C of theshaft 60 via openings defined in theshaft 60 fore of theseal 100. Nevertheless, theseal 100 may be said to be pressured on its fore side facing the second cavity B2. Due to the comparatively higher pressure borne by theseal 100 on its aft side facing the first cavity B1, an axial flow of hot, pressured air, referred to henceforth as a gap flow FG, occurs axially from the first cavity B1 across thebore 70 a of thedisc 70′ and thecorresponding seal 100 via the gap G. - Turning now to
FIG. 3 , in accordance with an aspect of the present technology, structural characteristics of an arrangement of theshaft 60, thedisc 70′ and theseal 100 will now be generally described with respect to an exemplary embodiment of therotor 50. The inner cavity C of theshaft 60 is a hollow interior surrounded by aninterior shaft surface 60 a of a generally cylindrical shape extending axially about a shaft axis that is coaxial with respect to the axis R. On the outside, anexterior shaft surface 60 b follows theinterior shaft surface 60 a, albeit defining portions having different radial profiles. For instance, theexterior shaft surface 60 b includes a portion referred to as anouter shaft surface 62 received by thedisc bore 70 a. Theouter shaft surface 62 has an outer diameter that is greater than that of an aft portion of theexterior shaft surface 60 b located aft of thedisc 70′. Theshaft 60 also includes anannular shaft groove 64 defined radially inwardly into theouter shaft surface 62. Theshaft groove 64 has an axial dimension (or width) and a radial dimension (or depth) sized for receiving theseal 100, as will be described hereinbelow. The width of theshaft groove 64 is defined axially between mutually facing walls (or surfaces) 64 a, 64 b of theshaft groove 64, namely afore groove wall 64 a and anaft groove wall 64 b. The depth of theshaft groove 64 is defined radially between theouter shaft surface 62 and abottom groove surface 64 c of theshaft groove 64. - On either side of the
shaft groove 64, theouter shaft surface 62 is circumscribed by diameters of different sizes, namely by a greater diameter on an aft side of theshaft groove 64 compared to that on the opposite side. As such, theaft groove wall 64 b is radially taller than thefore groove wall 64 a. Conversely, theshaft groove 64 may be said to be deeper adjacent to theaft groove wall 64 b than adjacent to thefore groove wall 64 a. It shall be noted that thedisc 70′ and theshaft 60 are arranged relative to one another such that the gap G has a similar radial size immediately fore and aft of theshaft groove 64. In some implementations, theouter shaft surface 62 tapers as it extends axially toward the aft side of theshaft groove 64 and/or tapers as it extends axially away from the fore side of theshaft groove 64. In other implementations, theouter shaft surface 62 is cylindrical on either side of theshaft groove 64, i.e., circumscribed by a same size diameter. In yet other implementations, theouter shaft surface 62 is circumscribed by two different size diameters on either side of theshaft groove 64. For instance, in the depicted embodiment, the diameter on the aft side is greater than that on the fore side. A side of theshaft groove 64 circumscribed by a greater diameter may be referred to as a load-bearing side of theshaft groove 64, corresponding to a portion of theshaft 60 adapted to be axially loaded via theseal 100 as will be described hereinbelow. - On an aft side of the
disc 70′, a portion (or disc projection) 70 b of thedisc 70, inside which thebore 70 a extends, projects axially.Such disc projection 70 b extends to an aft disc end 70 c of thedisc 70′. From the aft disc end 70 c, thedisc 70′ defines aninner disc surface 72 forming an aft portion of thebore 70 a. Theinner disc surface 72 extends fore relatively to the aft disc end 70 c, from a nearby aft end 72 b to afore end 72 a located adjacent to an annular cavity of thedisc 70′. Thedisc projection 70 b is sized and arranged relative to theshaft 60 such that theinner disc surface 72 axially overlaps theshaft groove 64, thereby circumscribing the gap G on either side of theshaft groove 64. It should be noted that in operation, therotor 50 will exhibit some degree of geometric variability, which may occur due to thermal expansion of rotor components and/or to built-in allowances. For example, theshaft 60 and thedisc 70′, despite being rotatable together about the axis R, can become temporarily displaced relative to one another in either axial direction relative to the axis R, for example during take off and/or climb, or during descent and/or landing. Such axial movement occurs in a range of movement defined between a first axial position and a second axial position, here respectively represented as first 60′ and second 60″ axial positions of theshaft 60 relative to thedisc 70′. - The
inner disc surface 72 is sized to overhang theouter shaft surface 62 on either side of theshaft groove 72 such that theshaft groove 64 is surrounded by a portion of theinner disc surface 72 in each of the first and secondaxial positions 60′, 60″. Such portion of theinner disc surface 72 is a rampeddisc profile 74, i.e., a shape extending radially relative to the axis R as it extends axially relative to the axis R. The rampeddisc profile 74 is arranged to be cooperable with a corresponding profile of theseal 100 so as to directionally load theshaft 60 via theseal 100 in an axial loading direction upon theseal 100 extending across the gap G from inside theshaft groove 64. The rampeddisc profile 74 ramps radially outwardly relative to the axis R as it extends in one axial direction relative to a central bore axis of thebore 70 a (here represented by the axis R coaxial thereto), this one direction corresponding to the axial loading direction. In the present embodiment, the rampeddisc profile 74 is a tapering profile which tapers at a taper angle G relative to the central bore axis (or axis R). The rampeddisc profile 74 has fore 74 a and aft ends 74 b and tapers as it extends from the aft end 74 b to the fore end 74 a. By way of this arrangement, the axial loading direction is the aft direction. The rampeddisc profile 74 can be configured such that the axial loading direction corresponds to an upstream direction, i.e., a direction away from a first cavity toward a second cavity exhibiting a positive pressure differential relative to the first cavity, as is the case for the cavity B1 relative to the cavity B2. Absent directional loading of theshaft 60 via theseal 100, the pressure differential may displace theseal 100 relative to theshaft groove 64 and to theinner disc surface 72, for example in an axial direction and/or even cocked at an angle to a radial direction relative to the axis R. Such misplacement of theseal 100 can open up circumferentially asymmetrical leakage paths outward and/or inward theseal 100, i.e., into the gap G and/or theshaft groove 64 around theseal 100. Theseal 100 can be provided in the form of asplit ring seal 100, i.e., an annular body having a split (or split joint) along its circumference. Near the split, the gap flow FG may exhibit singularities resulting in a circumferentially asymmetrical heat transfer along theshaft 60 on either side of theshaft groove 64, which may be further exacerbated upon theseal 100 being misplaced. Among possible outcomes, such asymmetrical flow conditions can induce thermal bowing of theshaft 60 which, in turn, may induce vibration of therotor 50 and of other elements of theengine 10 mechanically linked thereto. Axially loading theshaft 60 via theseal 100 axially positions theseal 100 relative to theshaft groove 64 and hence relative to gap-defining surfaces of therotor 50 nearby theshaft groove 60 such that the gap flow FG is circumferentially balanced. Axially positioning theseal 100 against eitherwall shaft 60. Such positioning of theseal 100 may correspond to a rated axial position of theseal 100 for a given operating condition of theengine 10 and/or a givenaxial position 60′, 60″ of theshaft 60 relative to thedisc 70′. - Still referring to
FIG. 3 , theexemplary seal 100 has a ring-like body extending circumferentially about a ring axis and axially relative to the ring axis between fore and aft ring sides 102 a, 102 b. Theseal 100 has aninner ring surface 102 c radially inward the ring axis between the ring sides 102, 102 b. Anouter ring surface 102 d of theseal 100 joins the ring sides 102 a, 102 b opposite theinner ring surface 102 c. At least a portion of theouter ring surface 102 d is shaped complementarily to the rampeddisc profile 74 and may thus be referred to as a rampedring profile 104 of theseal 100. Such complementarity between the rampeddisc profile 74 and the rampedring profile 104 results in the rampeddisc profile 74 imparting a normal force having a radial component and an axial component onto the rampedring profile 104 upon a radial force urging the rampedring profile 104 radially outwardly and against the rampeddisc profile 74. Stated otherwise, thedisc 70′ and theseal 100 are sized and arranged relative to one another such that in operation, as theengine 10 operates and thedisc 70′ expands radially outwardly due to a given centrifugal force and heating, theseal 100 expands radially outwardly under the given centrifugal force so as to load the rampedring profile 104 against the rampedring profile 74 of thedisc 70′. Such loading of the rampedring profile 104 against the rampeddisc profile 74 will also occur upon theseal 100 moving axially with theshaft 60 relative to thedisc 70′ in a direction opposite to the axial loading direction. In implementations where the width of theshaft groove 64 is greater than that of theseal 100, the axial component of the normal force resulting from such loading of the rampedring profile 104 against the rampedring profile 74 will induce some axial movement of theseal 100 relative to thedisc 70′ in the axial loading direction, to the extent allowed by theshaft groove 64. - The ramped
ring profile 104 has a shape extending radially relative to the axis R as it extends axially relative to the axis R. The rampedring profile 104 is arranged to be cooperable with the rampeddisc profile 74 so as to directionally load theshaft 60 via theseal 100 in the axial loading direction upon theseal 100 extending across the gap G from inside theshaft groove 64. The rampedring profile 104 ramps radially outwardly relative to the axis R as it extends in the axial loading direction relative to the ring axis (here represented by the axis R coaxial thereto). In the present embodiment, the rampedring profile 104 is a tapering profile which tapers at a taper angle relative to the ring axis (or the axis R), corresponding to the taper angle Θ of theramp disc profile 104. The rampedring profile 104 has fore 104 a and aft ends 104 b and tapers as it extends from the aft end 104 b to thefore end 104 a. Stated otherwise, theramp disc profile 104 can be described as a frustoconical shape, of which the fore 104 a and aft 104 b ends form first and second peripheral edges. An axial distance between the fore 104 a and aft 104 b ends defines a ring tapering length of the ramp disc profile 104 (or of the frustoconical shape). InFIG. 3 , it can be appreciated that a disc tapering length defined between the fore 74 a and aft 74 b ends is greater than the ring tapering length. Such difference in tapering lengths can be set to be at least equal to an axial distance between the first and secondaxial positions shaft 60 with theseal 100 relative to thedisc 70′, such that cooperation between theseal 100 and thedisc 70′ can occur across the range of motion. - In this embodiment, the axial loading direction is upstream, i.e., away from the cavity B2 and toward the cavity B1, and hence toward positive pressure and temperature gradients. Configuring the axial loading direction to be upstream (or aft) as opposed to downstream (or fore) can contribute to sealing performance, in some cases mitigating the extent and/or asymmetry of the heat transfer occurring in the
shaft 60 downstream of theshaft groove 64 via the gap flow FG. Still, in other embodiments, therotor 50 is arranged for the axial loading direction to be downstream. - The ring sides 102 a, 102 b and the
inner ring surface 102 c together define an inner ring shape of theseal 100 shaped complementarily to (or receivable by) theshaft groove 64. In embodiments, the inner ring shape of theseal 100 conforms to a bottom (or radially inner) shape of theshaft groove 64 such that theseal 100 may be seated into theshaft groove 64. Theseal 100 has an axial dimension (or width) and a radial dimension (or thickness) sized to be receivable by theshaft groove 64. The width of theseal 100 is defined axially between mutually facing walls (or surfaces) 64 a, 64 b of theshaft groove 64, namely afore groove wall 64 a and anaft groove wall 64 b. The thickness of theseal 100 is defined radially between theinner ring surface 102 c and theouter ring surface 102 d, and may be described as a difference between diameters respectively circumscribing theseal 100 inwardly and outwardly. - As mentioned hereinabove, the
seal 100 can be of a split ring type in some embodiments, i.e., a construction allowing resilient, radial expansion of theseal 100 under radial loading. Theseal 100 can thus be constructed of a resilient, strong and heat resistant material, such as for example metals, metallic alloys and metal matrix composites. In this embodiment, theseal 100 is expandable radially from a nominal (or baseline) diameter Φ of theseal 100. The diameter Φ corresponds to an inner disc diameter defined by theinner disc surface 72 in the rampeddisc profile 74 at a location between the ends 74 a, 74 b, respectively defining fore and aft inner disc diameters. Upon theshaft 60 being positioned at the firstaxial location 60′ with theseal 100 relative to thedisc 70′, theseal 100 is seated in theshaft groove 64 and extends radially outwardly across the gap G to the diameter Φ. In the firstaxial position 60′, the aft end 104 b of the rampedring profile 104 is circumscribed by the diameter Φ. Upon theshaft 60 being positioned at the secondaxial location 60″ with theseal 100 relative to thedisc 70′, theseal 100 is radially expandable to a diameter defined by the rampeddisc profile 74 at a location aft of the the diameter Φ, in this case the aft inner disc diameter at the aft end 74 b. In the secondaxial position 60″, theseal 100 is rotatable with theshaft 60 so as to expanded radially outwardly to the aft inner disc diameter, thereby closing the gap G. With the seal expanded to the aft inner disc diameter, moving theshaft 60 with theseal 100 from the secondaxial position 60″ to the firstaxial position 60′ urges theseal 100 to constrict radially to the diameter Φ. Under certain circumstances, radial deformation of thedisc 70′ will cause the size of thebore 70 a (and thus of the diameters of the inner disc surface 72) to change. Narrowing of thebore 70 a may thus urge theseal 100 to constrict radially and/or to move toward the axial loading direction and, conversely, widening of thebore 70 b may allow theseal 100 to radially expand and/or to move in the direction opposite to the axial loading direction. In the firstaxial position 60′, theseal 100 is seated (or bottomed out) into theshaft groove 64. In other embodiments, theshaft groove 64 is sized so as to conform to the inner shape of theseal 100 upon theseal 100 being constricted radially to a diameter defined by the rampeddisc profile 74 at a location fore of the diameter Φ, such as the fore inner disc diameter at the fore end 74 a. In yet other embodiments, the nominal diameter Φ of theseal 100 corresponds to the fore inner disc diameter. In other embodiments, either one or both of the rampeddisc profile 74 and the rampedring profile 104 can differ in shape, so long as a suitable geometric complementarity is provided. In some such embodiments, the ramped disc profile and the ramped ring profile can taper at slightly different angles or be locally non-congruent. Such a difference in taper angle may for example be in a range of 0.5 to 4 degrees. - With reference to
FIGS. 4-7 , further structural characteristics of theseal 100 will now be described. The embodiment of theseal 100 shown inFIG. 4 is of a split ring type, i.e., a seal having asplit joint 110. The seal (or split ring) 100 has a pair of mutually overlapped end portions (or ends) 112, 114 together defining the split joint 110, and a ring-likearcuate portion 116 extending between theends seal 100 is also provided with achannel 120 at a location diametrically opposite to the split joint 110 along thearcuate portion 116. Thechannel 120 is defined into theinner ring surface 102 d and extends axially through thearcuate portion 116. - The split joint 110 and the
channel 120 together form a diametrically-balanced axial flow path across theseal 100 via the split joint 110 and thechannel 120 upon theseal 100 conforming to a certain outer diameter. The ends 112, 114 are provided with complementary shapes being distensible to and from one another to allow theseal 100 to resiliently deform, whether by constriction or expansion. Constricting theseal 110 reduces a size of a joint flow path defined by the seal joint 110 and, conversely, expanding theseal 100 increases the size of the joint flow path. Hence, in some embodiments, thechannel 120 is sized, shaped and positioned relative to the split joint 110 such that a channel flow path of thechannel 120 corresponds to the joint flow path upon theseal 100 conforming to an outer diameter referred to as a graded diameter, which may be the nominal diameter Φ in certain embodiments. In other embodiments, theseal 100 is radially expandable to conform to the graded diameter. In yet other embodiments, theseal 100 is radially constrictable to conform to the graded diameter. - The
seal 100 is provided with features to minimize fretting. For instance, at least some of the edges at theends shaft 60, thedisc 70′ or with an opposite one of theends FIG. 3 , at least some of the edges of theseal 100 located circumferentially between theends ring surface 104, which are curved, and the edges adjacent to theinner ring surface 102 c in this case being chamfered. In some implementations, theseal 100 is constructed of an inherently low-friction material selected so as to minimize fretting. Theseal 100 can also be provided with a low-friction coating, for instance on portions of theseal 100 deemed prone to fretting. Likewise, suitable low-friction coating can be provided on portions of the disc bore 70 a and/or portions of theshaft 60 prone to frictionally engage with theseal 100, whether in use or during assembly. - Referring to
FIGS. 5A to 5C , exemplary configurations of the split joint 110 are shown. A distance δ is shown, schematically representing a distance between mutually-opposing surfaces of theends seal 100 corresponding to the nominal diameter Φ. In some such embodiments, theseal 100 is constrictable to a narrow diameter and expandable to a wide diameter. In the depicted embodiments, the narrow diameter corresponds to the fore inner disc diameter, at which the ends 112, 114 are interlocked, with a distance therebetween being than the distance δ. The wide diameter corresponds to the aft inner disc diameter, at which the ends are spaced by a distance greater than the distance δ. InFIG. 5A , theends surfaces FIG. 5B , theends surfaces FIG. 5C , theends FIGS. 6A, 6B , thechannel 120 may adopt an arcuate shape, although other shapes are contemplated. As shown inFIG. 6B , thechannel 120 may be formed of a plurality ofopenings outer ring surface 102 d. Depending on the embodiment, the shape and distribution of theopenings openings - With reference to
FIGS. 7 and 8 , therotor 50 can be provided with a plurality of seals, including at least oneadditional seal 100′ fitted toshaft 60 at a location fore of theseal 100. In some such embodiments, theshaft 60 has aforemost shaft groove 64′ located between a fore end of theouter shaft surface 62 and theshaft groove 64. The at least oneseal 100′ can thus be aforemost seal 100′ fitted into theforemost shaft groove 64′. Theseal 100 and theforemost seal 100′ can be fitted in thecorresponding shaft grooves seals seals channel 120′ of theforemost seal 100′ are respectively oriented (or clocked) at the azimuthal angle α relative to the split joint 110 and thechannel 120 of theseal 100. Hence, a flow path formed across the plurality of seals can be said to be indirect. In some embodiments, only one of theseal 100 and theforemost seal 100′ is provided with achannel 120. - In some embodiments, one or both of the
seals anti-rotational feature anti-rotational feature 66 associated with the correspondingshaft groove anti-rotational feature 66 of eachgroove seals corresponding shaft grooves - In
FIG. 8 , there is shown an exemplary embodiment of therotor 50 in which theshaft 60 is fitted with twoseals shaft groove 64 is fitted with theseal 100, and theshaft 60 also has anothergroove 64′ spaced axially relative to thegroove 64 and fitted with theseal 100′. Thegrooves outer shaft surface 64, and thus may be referred to as anaft groove 64 and aforemost groove 64′. Conversely, theseals aft seal 100 and aforemost seal 100′. Theinner disc surface 72 includes a foremost rampeddisc profile 74′ which defines a foremost inner disc diameter close to a fore end of theinner disc surface 72. In this embodiment, the foremost rampeddisc profile 74′ ramps (or in this case tapers) in a direction opposite to the direction in which the (aft) rampeddisc profile 74 tapers. Conversely, theforemost seal 100′ has a foremost rampedring profile 104′ cooperable with the foremost rampeddisc profile 74′ to directionally load theshaft 60 in an axial loading direction opposite to that associated with theaft seal 100. Hence, the foremost rampedring profile 74′ tapers away from the foremost inner disc diameter. As therotor 50 is provided with twoseals disc 70′ can cooperate with eitherseal shaft 60 moving axially relative to thedisc 70′ to axially load theshaft 60 via the oneseal shaft 60. It shall be noted that during assembly, theshaft 60 is fitted with theseals bore 70 a from the aft end 70 c of thedisc 70′. Hence, the depth of theforemost shaft groove 64′ is sized to be sufficient (or deep enough) for theseal 100′ to radially collapse clear of the aft rampeddisc profile 74 as theseal 100′ moves axially with theshaft 60 toward the foremost rampeddisc profile 74′. In this implementation, theseals foremost groove 64′ is deeper than theaft groove 64, although it is contemplated that theaft groove 64 could have a matching depth. - The embodiments described in this document provide non-limiting examples of possible implementations of the present technology. Upon review of the present disclosure, a person of ordinary skill in the art will recognize that changes may be made to the embodiments described herein without departing from the scope of the present technology. For example, the
rotor 50 may correspond, mutatis mutandis, to any other rotor of a gas turbine engine having concentric rotor parts defining a radial gap therebetween in fluid communication between cavities of the rotor at different pressures. Such rotors may for example be in theturbine section 18 or in an accessory gearbox of theengine 10. Yet further modifications could be implemented by a person of ordinary skill in the art in view of the present disclosure, which modifications would be within the scope of the present technology.
Claims (20)
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US17/177,585 US11542819B2 (en) | 2021-02-17 | 2021-02-17 | Split ring seal for gas turbine engine rotor |
CA3149070A CA3149070A1 (en) | 2021-02-17 | 2022-02-15 | Slpit ring seal for gas turbine engine rotor |
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US17/177,585 US11542819B2 (en) | 2021-02-17 | 2021-02-17 | Split ring seal for gas turbine engine rotor |
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US20220259975A1 true US20220259975A1 (en) | 2022-08-18 |
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US11892083B2 (en) * | 2022-04-06 | 2024-02-06 | Rtx Corporation | Piston seal ring |
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CA3149070A1 (en) | 2022-08-17 |
US11542819B2 (en) | 2023-01-03 |
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